CONNECTION OF A FUSELAGE TO AN AIRCRAFT WING

Abstract

A wing box rib (13), joining an aircraft wing (3) to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage (2), having in particular an upper line (14) situated above a junction line (15) of the wing upper surface panel (3). The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favourable manner.

Description

TECHNICAL FIELD

The subject matter of the present invention is the area of connection of a fuselage to an aircraft wing.

The conventional mode of connection comprises, as is represented in FIG. 1, a connection piece 1 of cruciform section at the junction of a panel of the fuselage 2, of a wing upper surface panel 3, of a wing box upper surface panel 4 extending the preceding panel, and of a rib 5 of the wing box extending the fuselage 2 while extending under it. Brackets 6 rest on the fuselage 2, and the upper surface panels 3 and 4 under the connection piece 1 to ensure a transmission of stress between the upper surface panels 3 and 4, being linked to said panels and also linked together through the rib 5 and the lower wing of the connection piece 1, with bolts 7. The rib 5 extends downwards up to a lower surface T-piece 8 through which it is connected to a wing lower surface panel 9 and a wing lower surface panel box 10. The assembly is completed by a lower surface backing plate that clamps the lower surface panels 9 and 10 together and the lower surface T-piece 8. Such connections appear in the prior documents FR-A-2 916 417 and FR-A-2 936 489.

FIG. 2 shows that the rib 5 has a contour that hugs the section of the wing and which is thus irregular. It is joined to the fuselage 2 by an upper junction line 12, curved and of variable height, extending typically over several adjacent panels 2a and 2b of the fuselage 2. It is further joined to a slanting frame panel 20 by a rear edge 21. The slanting frame panel 21 is joined to one of the panels 2b of the fuselage by an upper edge 22.

This design is complicated, and gives a connection quite long to manufacture, and which is in addition heavy. The aim of the invention is to propose a different connection, simplified with respect to the prior design.

In a general manner, the invention relates to a connection of a fuselage to an aircraft wing, the wing comprising a rib extending the fuselage and a wing upper surface panel joined to the rib, characterised in that the rib extends above the wing upper surface panel and is joined to the fuselage at an upper line higher than a junction line from the wing upper surface panel to the rib.

The projecting rib enables an assembly to other fuselage panels over a contour simpler than that of the upper line 12 of FIG. 2. The junction of the rib to the fuselage is facilitated. The connection piece 1 with cruciform section disappears and the assembly is simplified.

The structure of the aircraft is not substantially weakened despite the omission of the connection piece 1 since the stresses of the wing remain transmitted to the rest of the aircraft by the wing box through the rib. The simplification of the assembly can, quite the opposite, lead to reinforcing it as regards the risks of rupture through fatigue or through corrosion of the assemblies.

An important advantage of the invention is that the upper line is advantageously horizontal and may thus be assembled very easily to the rest of the fuselage, especially if said upper line belongs to a junction line of two horizontal strips of panels of said fuselage. In an even better manner, the upper line can extend to a neutral bending line of the aircraft in a vertical plane, which considerably reduces the stresses.

The simplification of the structure of the aircraft is more extensive if the rib further encompasses a slanting frame panel.

A satisfactory fastening of the wing to the wing box is re-established if the wing upper surface panel and the wing box upper surface panel extending it are joined by brackets resting on the rib to an upper face and to a lower face of said upper surface panels, and assembled with bolts traversing the rib, thus replacing the link procured by the connection piece 1.

Such a connection is particularly advantageous with a fuselage made of composite material, since no panel then needs to be assembled to the connection piece 1 near the wing and wing box upper surface panels, where the stresses are important.

Another aspect of the invention is an aircraft provided with a connection according to the preceding description.

The invention will now be described in a purely illustrative manner with reference to the figures, among which:

FIGS. 1 and 2, already described, represent a known connection of a fuselage to an aircraft wing,

and the other FIGS. 3, 4 and 5 illustrate an embodiment of the invention, FIG. 3 illustrating the connection, FIG. 4 the installation of the rib on the aircraft, and FIG. 5 the arrangement of the rib on the fuselage.

Reference is made to FIGS. 3 and 4. The rib according to the invention bears the reference (13) and henceforth has a greater extension than the section of the wing: its upper line (14) of junction to the fuselage (2) is above the junction line (15) to the upper surface panel (3 and 4). Said upper line is advantageously horizontal in order to be connected easily to the panels of the fuselage (2), and even more advantageously to the junction of two horizontal strips of said panels, strips denoted (2i and 2j) in FIG. 5, and, in an even more advantageous manner, at a height corresponding to the neutral bending line of the fuselage in a vertical plane, which thereby reduces the constraints exerted on the rib (13) and more particularly on the junction line.

The connection piece (1) is, as is represented in FIG. 3, replaced by two additional brackets (16) similar to the other brackets (6) but established on the upper faces of the upper surface panels (3 and 4), again with bolts (17) to link them together through the rib (3) making a transmission of stresses possible.

The rib (13) may also be extended towards the rear with respect to the known rib (5), henceforth encompassing the slanting frame panel (20); its rear edge (23) is then itself also connected to the fuselage (2). It is obvious that the integration of a part of the surface area of the fuselage in the rib (13), which is achieved in this invention, gives a more coherent connection, the fuselage panels being regular and the shape irregularities being all grouped together on the rib, which is in any case a part intended to absorb considerable stresses. The extension of the surface area of the rib also avoids that other parts of the aircraft, less resistant, are adjacent to the wing and to the stresses that pass through it. The manufacture of the aircraft itself must be simplified. The thermal stresses in the connection area, due to differential expansions, are considerably reduced or eliminated, as are problems linked to galvanic corrosion not just during routine use but also during assembly. These different advantages make it possible to construct more easily the fuselage made of composite material.

Claims

1. Connection of a fuselage to an aircraft wing, the wing comprising a rib extending the fuselage and a wing upper surface panel joined to the rib, characterised in that the rib (13) extends above the wing upper surface panel (3) and is joined to the fuselage (2) at an upper line (14) higher than a junction line (15) from the wing upper surface panel to the rib.

2. Connection of a fuselage to an aircraft wing according to claim 1, characterised in that the upper line (14) is horizontal.

3. Connection of a fuselage to an aircraft wing according to claim 2, characterised in that the upper line (14) belongs to a junction line of two horizontal strips (2i, 2j) of panels of the fuselage (2).

4. Connection of a fuselage to an aircraft wing according to claim 3, characterised in that the upper line extends to a neutral bending line of the aircraft in a vertical plane.

5. Connection of a fuselage to an aircraft wing according to claim 1, characterised in that the wing upper surface panel (3) and a wing box upper surface panel (4) extending it are joined by brackets (16) resting on the rib at an upper face and a lower face of said upper surface panels, and assembled with bolts (17) traversing the rib (13).

6. Connection of a fuselage to an aircraft wing according to claim 1, characterised in that the rib encompasses a slanting frame panel (21).

7. Aircraft, comprising a fuselage, a wing and a connection of the fuselage to the wing, said wing comprising a rib extending the fuselage and a wing upper surface panel joined to the rib, characterised in that the rib (13) extends above the wing upper surface panel (3) and is joined to the fuselage (2) at an upper line (14) higher than a junction line (15) from the wing upper surface panel to the rib.

8. Aircraft according to claim 7, characterised in that the fuselage (2) is made of composite material.